uaa rocketry pdr presentation nasa student launch 2014-2015
TRANSCRIPT
Vehicle Dimensions● Overall Length 77.7 inches● Body tube diameter 4 inches
and 0.0625 inch thickness
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Vehicle Materials
● 4 inch 5:1 VonKarmen Filament wound nose cone
● Filament wound ProFusion body and coupler tubing
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Vehicle Materials● Fins and centering rings cut
from 0.1875 inch structural fiberglass
● Motor tube made from wound G12 fiberglass tubing
● Bulkheads and payload compartment CNC cut from 0.125 inch structural fiberglass
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Vehicle Materials
● ¼”-20 stainless steel full threaded rods
● Grade-8 ¼ ”-20 Nylon-insert flanged locknuts
● 0.25 inch foged steel Eyebolts
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Vehicle Justifications
● Conventional configuration: Nose cone/Payload Compartment, Central Section, and Booster Section
● Aft Nose Cone/Payload section serves as payload ejection mechanism● Dual deployment; drogue and payload ejections simultaneous to
simplify design
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Safety Testing Plans
● AGSE components will be constructed with ample time left to thoroughly test system safety, effectiveness, and consistency
● Extensive ground testing performed to ensure ejection charges perform deployment operations safely and consistently
● Subscale and full-scale launch vehicles will be test launched early and often at Alaska Northstar (NAR) launch events
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Stability Analysis
● Center of Pressure: 59.28 inches from nose● Center of Gravity: 51.42 inches from nose● Static Stability Margin: 1.95● Thrust-to-Weight Ratio: 5.5:1● Rail Exit Velocity: 33.4 feet/second
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Test Plan Overview
● AGSE components to be constructed and tested at UAA Design Studio● Ejection Charges to be tested outdoors adjacent to Design Studio● Subscale and full scale launch events at Lake Louise and Big Lake
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Launch Pad Discussion
● Launch rail is 8020-1530 Aluminum extrusion 180 inches in length● Feet are adjustable to level the apparatus● Declination of launch rail is calibrated to 5 degrees from vertical● Blast pad safely deflects exhaust gases away from grass
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Motor Compartment Dimensions/Discussion● 54 millimeters in diameter and 13 inches in length to accommodate J
sized motor● Motor compartment is G12 wound fiberglass made by ProLine
Rocketry Inc. ● Compartment is bonded to centering rings using JB Weld
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Drogue Parachute Discussion
● Located between booster and central sections● Parachute is a 2 foot Rocketman Parachute● Tethered to rocket with ¼” Aramid rope
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Deployment System Discussion
● Entire aft section will deploy simultaneously with main chute at 1000 feet AGL
● Aft section will descend under a 3 foot Rocketman Parachute
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Payload Compartment Discussion
● Payload compartment is CNC cut from 0.125” structural fiberglass, bonded with West Systems Epoxy
● Hatch is actuated by two servos at opposite ends of the compartment● Over-center geometry of hatch respective to servo motor prevents
hatch from opening
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Main Chute Discussion
● The main chute will deploy at 1000 feet AGL● Chute is a 60 inch Iris Ultra Parachute made by Fruit
Chutes● Parachute is sized to allow central and booster
sections to descend with kinetic energy ≤ 75 ft-lbf● Chutes and rocket sections tethered with ¼ inch
Aramid Rope
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Recovery System Discussion
● First ejection charge at apogee; booster section and central section separate to deploy drogue chute
● Second and third ejection charges at 1000 feet AGL:o Aft nose cone/payload section descend separately o Central and booster sections descend under drogue chute and main chute
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Nose Cone Drawing/Discussion
Image credit to performancehobbies.com [1]
● 4 inch 5:1 Von Karmen Filament Wound Nose Cone
● Connected to payload compartment
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Tail Fin Drawing/Discussion
● Fins cut from 0.1875 inch structural fiberglass
● Delta-style shape● Dimensions:
o 12 inch root cord o 8 inch tip cord o 5 inch heighto 2 inch sweep length
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AGSE Overview• Control
– Spatial Constraints– Degrees of Freedom – Precision and accuracy
• Components – Base Structure– Arm– End Effector
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Base Structure
• Control Overview– Spatial Constraints
• Retain rocket during payload insertion
– fixed dimensional relationship
– Precision and accuracy• Primary mounting point
for the arm structure
• Contains all electronics and power systems 29
Arm• Control Overview
– Spatial Constraints• Of sufficient height to
remain clear of Launch Vehicle
– 1 degrees of freedom• Boom: Rotation – Yaw
– Precision and accuracy • Position
switches/sensors30
Linear Motion System• Control
– Spatial Constraints• Of sufficient length to
clear the base station• Of sufficient length to
reach the ground– 1 Degree of Freedom
• LMS: Translation - Heave– Precision and accuracy
• Ground sensing capability 31
End Effector• Control
– Spatial Constraints• Of sufficient width to
capture a 6” area – Precision and accuracy
• Closing pressure detection
• Orientation of capture
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AGSE Integration and Testing• 3D component models• Assembly checks – QC• Iterative testing at subsystem and system
levels • Sensor/program testing de-bugging
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